Abstract
Detailed surface heat transfer and pressure distributions have been obtained in three-dimensional shock-wave boundary-layer interactions flow regions. The data described were obtained on fundamental shapes: planar wings with trailing edge flaps or spoilers and planar or cylindrical center bodies, representative of the aft portion of hypersonic aircraft. An overview of the work is presented; details of the projects are available in many reports in the open literature. Analytic, empiric methods are advanced for predicting the extent of separation and the increased heat transfer and pressure loads in three-dimensional separated flow regions.
Keywords
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.
This is a preview of subscription content, log in via an institution.
Buying options
Tax calculation will be finalised at checkout
Purchases are for personal use only
Learn about institutional subscriptionsPreview
Unable to display preview. Download preview PDF.
Abbreviations
- b:
-
span
- h:
-
step height, or heat transfer rate coefficient
- HL:
-
hinge line
- \(\ell\) :
-
lenght of separation
- M:
-
Mach Number
- p:
-
pressure
- Re:
-
Reynolds number based on local flow conditions
- x, y, z:
-
rectangular coordianates
- β:
-
ratio of specific heats for air
- ε:
-
flow of specific heats for air
- ;:
-
shock wave angle
References
Kaufman, L.G. II, Meckler, L. and Hartofilis, S. A., “An Investigation of Flow Separation and Aerodynamic Controls at Hypersonic Speeds,” J. of Aircraft, AIAA, Vol 3, No. 6, Nov 1966.
Korkegi, R.H., “Survey of Viscous Interactions Associated with High Mach Number Flight,” AIAA J., Vol. 9, No. 5, May 1971.
Kaufman, L.G. II and Gleitsmann, F.G.W., “Descriptive Survey of High Speed Flow Separation,” AFWAL TM 83-174-FIMG, Wright-Patterson AFB, March 1983 Grumman R&D Center Report RM-782, December 1983.
Clark, R.L., Kaufman, L.G. II and Maciulaitis, A., “Aeroacoustics Measurements for Mach 0.6 to 3.0 Flows Past Rectangular Cavities,” AIAA Paper 80-0036, Jan 1980.
Kaufman, L.G. II, Maciulaitis, A. and Clark, R.L., “Mach 0.6 to 3.0 Flows Over Rectangular Cavities,” AFWAL TR 82-3112, Wright-Patterson AFB, May 1983.
Kaufman, L.G. II, “Hypersonic Flows Past Transverse Jets,” J. Spacecraft and Rockets, Vol. 4, No. 9, Sept 1967.
Johnson, C.B. and Kaufman, L.G. II, “Incident Shock Interactions with Boundary Layers,” J. Spacecraft and Rockets, AIAA, Vol 12, No. 6, June 1975.
Kaufman, L.G. II, Korkegi, R.H. and Morton, L.C., “Shock Impingement Caused by Boundary-Layer Separation Ahead of Blunt Fins, ” AIAA Jr, Vol 11, No. 10, Oct 1973.
Kaufman, L.G. II and Kirchner, R.D., “High Speed Flow Separation Ahead of Finite Span Steps,” AFFDL TR 78-30, Wright-Patterson AFB, April 1978.
Kaufman, L.G. II and Freeman, L.M., “Separation Ahead of Steps on Swept Wings,” J. of Ai rcraft, AIAA, Vol 13, No. 12, Dec 1976.
Kaufman, L.G. II and Freeman, L.M., “Separation Ahead of Controls on Swept Wings,” ARL TR 75-0134, Wright-Patterson AFB, June 1975.
Kaufman, L.G. II and Johnson, C.B., “Aerodynamic Heating Rate Distributions Induced by Trailing Edge Controls on Hypersonic Aircraft Configurations at Mach 8,” Grumman Aerospace Corp, R&D Center Report RM-799, NASA TM 8753, Aug 1984.
Kaufman, L.G. II and Johnson, C.B., “Methods for Estimating Pressure and Thermal Loads Induced by Elevon Deflections on Hypersonic Vehicle Surfaces with Turbulent Boundary Layers,” NASA TM 83130, Langley, Sept 1981.
Johnson, C.B. and Kaufman, L.G. II,“High Speed Interference Heating Loads and Pressure Distributions Resulting from Elevon Deflections,” J. Aircraft, AIAA, Vol 17, No. 3, March 1980.
Kaufman, L.G. II and Johnson, C.B., “Pressure and Thermal Distributions on Wings and Adjacent Surfaces Induced by Elevon Deflections at Mach 6,” NASA TP 1356, Langley Research Center, March 1979.
Ames Research Staff, “Equations, Tables, and Charts for Compressible NACA Report 1135,” 1953.
Hayes, James R., “Prediction Techniques for the Characteristics of Fin Generated Three Dimensional Shock Wave Turbulent Boundary Layer Interactions,” AFFDL TR 77-10, Wright-Patterson AFB, May 1977, available from DTIC as AD A042 024.
Author information
Authors and Affiliations
Editor information
Editors and Affiliations
Rights and permissions
Copyright information
© 1986 Springer-Verlag Berlin, Heidelberg
About this paper
Cite this paper
Kaufman, L.G., Johnson, C.B. (1986). An Overview of some Investigations of Pressure and Thermal Distributions Induced by Trailing Edge Controls on Hypersonic Aircraft. In: Délery, J. (eds) Turbulent Shear-Layer/Shock-Wave Interactions. International Union of Theoretical and Applied Mechanics. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-82770-9_32
Download citation
DOI: https://doi.org/10.1007/978-3-642-82770-9_32
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-642-82772-3
Online ISBN: 978-3-642-82770-9
eBook Packages: Springer Book Archive